阅读说明：本技术 一种导流板深度修理过程中的安装定位方法 (Installation positioning method in deep repair process of guide plate ) 是由 万绍钦 李强宣 鲁光涛 佘繁超 李建伟 朱珊珊 徐艳荣 石双 盖晓峰 李芳宇 高 于 2021-09-27 设计创作，主要内容包括：本发明涉及一种导流板深度修理过程中的安装定位方法,包括以下相继进行的方法步骤：a)在原机导流板未拆解前采用三维扫描仪对机上安装状态进行取样扫描；b)机下测绘；c)对导流板接头进行逆向建模得出导流板胶接模具；d)将首架机导流板接头技术状态与上述步骤c中导流板胶接模具比对分析；e)若上述步骤d中两者相匹配,则使用导流板胶接模具将定位槽型梁的位置做好标记,然后以梁为基准验核蜂窝芯的位置,在蜂窝芯与胶接模具完全贴合后做好标识,再以蜂窝芯和梁的位置为基准制定位孔定位蒙皮、肋的位置；f)将定位完成的蒙皮、肋进行磷酸阳极氧化,铺贴胶粘剂,装配封装后进行热压罐胶接；g)对导流板进行装配及机上验核并装机使用。(The invention relates to an installation and positioning method in a deep repair process of a guide plate, which comprises the following sequential method steps: a) before the original machine guide plate is not disassembled, a three-dimensional scanner is adopted to carry out sampling scanning on the installation state of the machine; b) surveying and mapping under a machine; c) performing reverse modeling on the guide plate joint to obtain a guide plate gluing mold; d) c, comparing and analyzing the technical state of the first frame machine guide plate joint with the guide plate gluing mold in the step c; e) if the two are matched in the step d, marking the position of the positioning groove type beam by using a guide plate gluing mold, checking the position of the honeycomb core by taking the beam as a reference, marking after the honeycomb core is completely attached to the gluing mold, and setting the positions of skin and ribs of the positioning hole by taking the positions of the honeycomb core and the beam as a reference; f) performing phosphoric acid anodic oxidation on the positioned skin and ribs, paving an adhesive, assembling and packaging, and performing autoclave bonding; g) and assembling the guide plate, checking on the machine and installing the guide plate for use.)

1. A mounting and positioning method in the deep repair process of a flow guide plate is characterized by comprising the following sequential method steps:

a) before the original machine guide plate is not disassembled, a three-dimensional scanner is adopted to carry out sampling scanning on the installation state of the machine;

b) detaching the guide plate from the airplane for performing under-the-air mapping;

c) b, performing reverse modeling on the air deflector joint by using the data in the steps a and b to obtain an air deflector gluing mold;

d) c, comparing and analyzing the technical state of the first frame machine guide plate joint with the guide plate gluing mold in the step c, and judging whether the two are matched;

e) if the two are matched in the step d, marking the position of the positioning groove type beam by using a guide plate gluing mold, checking the position of the honeycomb core by taking the beam as a reference, marking after the honeycomb core is completely attached to the gluing mold, and setting the positions of skin and ribs of the positioning hole by taking the positions of the honeycomb core and the beam as a reference; if the two are not matched, adjusting the guide plate gluing mold until the guide plate gluing mold is matched;

f) performing phosphoric acid anodic oxidation on the positioned skin and ribs, then paving an adhesive, assembling and packaging, and performing autoclave bonding;

g) assembling the guide plate and performing on-machine check;

h) the guide plate is installed for use.

2. The method for installing and positioning the flow guide plate in the deep repair process of the flow guide plate as claimed in claim 1, wherein: in the method step e), if the two are not matched, adjusting the guide plate gluing mold according to the following method;

s1) arranging positioning holes on the guide plate gluing mould again,

s2) trimming the guide plate gluing mold,

s3) redrawing the outline of the guide plate on the guide plate gluing mold according to the position relation of the crossbeam, the end rib and the tail edge of the guide plate gluing mold.

3. The method for installing and positioning the flow guide plate in the deep repair process of the flow guide plate as claimed in claim 1, wherein: spraying the air deflector after the method step g) is completed.

4. The method for installing and positioning the flow guide plate in the deep repair process of the flow guide plate as claimed in claim 1, wherein: in the method step d), the first aircraft is an aircraft designed for the original aircraft deflector mold.

Technical Field

The invention relates to the technical field of deep repair of guide plates of large-scale transport planes, in particular to an installation and positioning method in the deep repair process of guide plates.

Background

After many years of flying use of large-scale transport aircraft, faults such as corrosion of a diversion plate surface skin or a honeycomb, skin cracks, surface pits, corrosion of a channel beam and the like frequently occur, and the repair tolerance specified by a major repair guideline is exceeded. In order to ensure the normal use of the airplane, the guide plate needs to be repaired deeply. The technical state difference between the original machine profile and the existing cementing mould is found in the deep repair process of the guide plate, meanwhile, the installation joint and the profile of the airplane are deformed to different degrees after the airplane is used for many years, and if the positioning reference of the existing cementing mould is adopted, the risk that the repaired workpiece is interfered with other parts and even cannot be installed for use exists.

Therefore, an installation and positioning method in the deep repair process of the guide plate is needed to ensure that the repaired part is consistent with the technical state of the original machine.

Disclosure of Invention

The invention provides an installation positioning method in a deep repair process of a guide plate, aiming at the technical problems in the prior art.

The technical scheme for solving the technical problems is as follows: an installation positioning method in the deep repair process of a flow deflector comprises the following sequential method steps:

a) before the original machine guide plate is not disassembled, a three-dimensional scanner is adopted to carry out sampling scanning on the installation state of the machine;

b) detaching the guide plate from the airplane for performing under-the-air mapping;

c) b, performing reverse modeling on the air deflector joint by using the data in the steps a and b to obtain an air deflector gluing mold;

d) c, comparing and analyzing the technical state of the first frame machine guide plate joint with the guide plate gluing mold in the step c, and judging whether the two are matched;

e) if the two are matched in the step d, marking the position of the positioning groove type beam by using a guide plate gluing mold, checking the position of the honeycomb core by taking the beam as a reference, marking after the honeycomb core is completely attached to the gluing mold, and setting the positions of skin and ribs of the positioning hole by taking the positions of the honeycomb core and the beam as a reference; if the two are not matched, adjusting the guide plate gluing mold until the guide plate gluing mold is matched;

f) performing phosphoric acid anodic oxidation on the positioned skin and ribs, then paving an adhesive, assembling and packaging, and performing autoclave bonding;

g) assembling the guide plate and performing on-machine check;

h) the guide plate is installed for use.

Preferably, in the above method for installing and positioning the deflector in the deep repair process, in step e), if the deflector and the mold do not match, the deflector gluing mold is adjusted according to the following method;

s1) arranging positioning holes on the guide plate gluing mould again,

s2) trimming the guide plate gluing mold,

s3) redrawing the outline of the guide plate on the guide plate gluing mold according to the position relation of the crossbeam, the end rib and the tail edge of the guide plate gluing mold.

Preferably, the method for installing and positioning the air deflector in the deep repair process of the air deflector is used, wherein the air deflector is painted after the step g) of the method is finished.

Preferably, in the above installation and positioning method during deep repair of the deflector, in step d), the aircraft used for the original aircraft deflector mold is designed by the first aircraft.

The invention has the beneficial effects that:

1. the process can ensure that the newly manufactured variable-curvature hyperbolic movable wing surface is consistent with the technical state of the original machine, and the joint of the new variable-curvature hyperbolic movable wing surface is matched with the height of the airplane in the subsequent assembly process.

2. The process method can ensure that the molded surface is more attached to the mold, improve the bonding quality of products, remarkably improve the qualification rate of products subjected to deep repair, reduce the defects of the products caused by bonding, simultaneously reduce the difficulty of assembly work, and ensure that the products have longer service life and are more durable in the subsequent use process.

3. The process method can be used for the subsequent batch repair and manufacture of the airplanes, and meanwhile, the process method can be popularized and applied to the replacement, repair and manufacture of other airplane similar movable parts, and has remarkable military benefits.

4. The three-dimensional scanner is adopted to carry out three-dimensional modeling on the mounting joint of the movable wing surface of the original machine on the machine and carry out modeling precision check, so that the assembly precision can be effectively improved, the subsequent debugging and mounting work of the product is reduced, and the one-time qualification rate of the product is improved.

5. The process can enable old parts to be matched with the molds, the same set of molds can be used for airplanes of different batches, the molds do not need to be manufactured again, and a large amount of manpower, material resources and financial resources are saved.

Drawings

FIG. 1 is a schematic view of the external configuration of a baffle;

FIG. 2 is a schematic view of the internal structure of a baffle;

fig. 3 is a schematic structural view of a deflector glue joint mold.

In the drawings, the components represented by the respective reference numerals are listed below:

1. the guide plate glue joint die comprises a guide plate glue joint die body 2, a honeycomb unit body 3, a honeycomb core 4, a lower skin 5, an upper skin 6, an inner joint 7, a crossbeam 8 and an outer joint.

Detailed Description

The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.

As shown in fig. 1, 2 and 3, in the drawings, the reference numeral 1 is a guide plate gluing mold, 2 is a honeycomb unit body, 3 is a honeycomb core, 4 is a lower skin, 5 is an upper skin, 6 is an inner joint, 7 is a girder, and 8 is an outer joint.

An installation positioning method in the deep repair process of a flow deflector comprises the following sequential method steps:

a) before the original guide plate of the machine is not disassembled, a three-dimensional scanner is adopted to carry out sampling scanning on the installation state of the machine. Specifically, after the airplane enters a factory, when the guide plate is not detached from the airplane, the flap is put down, the three-dimensional scanner is used for scanning the joint of the guide plate, before scanning, a second-level encryption measurement control network is established by adopting an MPS single-camera photogrammetry system, and the point cloud rapid scanning surveying and mapping work of the components is carried out by adopting a rapid scanning measurement system. 3 monitoring measuring points are uniformly distributed on the wingtips of any wing, the change of the wingtips of the wings is detected by adopting a laser tracker, the monitoring is carried out for more than 30min before the start of work, the detection interval is 5mm every time, the position change of the monitoring points is required to be not more than 0.03mm, the monitoring is carried out once every 30 min-40 min after the start of mapping, the position change of the monitoring points is required to be not more than 0.03mm, and the on-board mapping state inspection is completed. And collecting data of the state guide plate on the machine.

b) And detaching the guide plate from the airplane for mapping under the airplane. The method specifically comprises the following steps of disassembling the guide plate from the airplane, inserting equal-direct bolts into bolt holes of each joint of the guide plate, and acquiring point cloud data of the guide plate in the off-airplane state according to the requirements in the step a.

c) And (c) performing reverse modeling on the guide plate joint by using the data in the steps a and b to obtain the guide plate gluing mold. The specific operation is as follows:

1) and respectively importing the scanning point cloud data of the on-board state of the deflector and the scanning point cloud data of the off-board state into the Geomagic Studio software, removing noise, repairing grids, simplifying data and splicing data, and storing the processed point cloud data.

2) And (4) importing the processed point cloud data of the off-machine state guide plate and the on-machine state guide plate into Design X software, and modifying and combining the two groups of data by taking bolt holes of the on-machine state guide plate as a reference.

3) The defects of the guide plate are compensated by combining the characteristics of the product due to the defects of pits, debonding and the like in the manufacturing and using process of the guide plate.

4) And drawing a draft of the honeycomb unit body of the guide plate by taking the guide plate bolt hole as a reference to obtain the outline.

5) And (3) taking the cross section contour as a stretching basis, stretching the whole contour in the tail edge contour line as a stretching direction to obtain the whole contour, projecting the point cloud contour by taking the central symmetry plane as a reference plane, determining the boundary of the skin and the channel beam, and cutting to obtain the surface skin and the channel beam surface.

6) And (3) obtaining the surface of the end rib by surface skin and surface offset of the channel beam, selecting the better fitting point cloud condition of other surfaces according to the point cloud, fitting the point cloud condition into a plane, and finally cutting according to the point cloud boundary to obtain the surface of the end rib.

7) And giving thicknesses to the obtained surface skin, the surface of the groove-shaped beam and the surface of the end rib to finish the establishment of the shape digital code.

d) And c, comparing and analyzing the technical state of the first machine guide plate connector with the guide plate gluing mold in the step c, and judging whether the first machine guide plate connector and the guide plate gluing mold are matched, wherein the first machine guide plate connector is an airplane designed for the original guide plate mold.

The specific operation steps are as follows:

1) and leading the established guide plate data and the guide plate gluing mold digital model into Design X software.

2) And (3) mounting the guide plate on the guide plate gluing mold in Design X software by taking one of the joint bolt holes as a datum point.

3) And detecting and analyzing the position relation between other joints of the guide plate and the joint of the guide plate gluing mold on Design X software, and recording specific numerical values.

4) And detecting and analyzing the matching of the molded surface of the guide plate and the guide plate gluing mold on Design X software, and recording specific numerical values.

5) And detecting and analyzing the position relation between the tail edge of the guide plate and the guide plate gluing mold on Design X software, and recording specific numerical values.

6) And detecting and analyzing the position relation between the crossbeam of the guide plate and the guide plate gluing mold on Design X software, and recording specific numerical values.

7) And detecting and analyzing the position relation between the short ribs of the guide plate and the guide plate gluing mold on Design X software, and recording specific numerical values.

e) If the two are matched in the step d, marking the position of the positioning groove type beam by using a guide plate gluing mold, checking the position of the honeycomb core by taking the beam as a reference, marking after the honeycomb core is completely attached to the gluing mold, and setting the positions of skin and ribs of the positioning hole by taking the positions of the honeycomb core and the beam as a reference; if the two are not matched, the guide plate gluing mold is adjusted, and the specific adjusting steps are as follows:

s1) arranging positioning holes on the guide plate gluing mould again,

s2) trimming the guide plate gluing mold,

s3) redrawing the outline of the guide plate on the guide plate gluing mold according to the position relation of the crossbeam, the end rib and the tail edge of the guide plate gluing mold.

The above steps are completed until the two are matched. After matching, checking the position of the honeycomb core by taking the beam as a reference, requiring the honeycomb core to be completely attached to the gluing mold, and setting the positions of the skin and the rib by taking the positions of the honeycomb core and the beam as the reference.

f) And (3) performing phosphoric acid anodic oxidation on the positioned skin and rib, then paving an adhesive, assembling and packaging, and performing autoclave bonding.

g) And assembling the guide plate and performing on-machine check. The specific operation is as follows:

1) assembling the guide plate, riveting and sealing each unit body according to a digital model, and then butting the unit bodies together.

2) And (4) checking the airplane after the butt joint is finished, and installing all the fasteners and the pull rods after the connector is matched without errors.

3) And spraying paint on the guide plate.

h) The guide plate is installed for use. And after the guide plate is assembled, and after the retraction test has no faults such as interference abnormal sound and the like, the guide plate can be assembled for use.

While one embodiment of the present invention has been described in detail, the description is only a preferred embodiment of the present invention and should not be taken as limiting the scope of the invention. All equivalent changes and modifications made within the scope of the present invention shall fall within the scope of the present invention.